Aircraft



1936. 4 A. v. S'ANTARSIERO 2,059,610

AIRCRAFT Original Filed Dec.- 28, 1934 Inventor rnt nia uev. 3, .1936

dunno STATE-S PATENT OFF-ICE Application'December 2a, 1934, Serial No.14!) Renewed September 19, 1936 2 Claims. (cyan-12) .This invention relates to amend and has; for

its object the provision of means for enablingthe craft to rise and descend vertically, and for improving the efliciency and enhancing the safety 5 or flight.

This specification contains subject matter common to my patent. Serial #1,988,9l9.

visi 'oilouvresin the wing or air foil and hinged panels normally closing said louvres for horizontal flight; but being arranged .to be positively opened, reducing thawing or air foil to a mere .frameworkior minimizing the resistance to vertical flight. v 15 A further objectoif the invention is a control system so arranged that the hinged panels have freedom oi. movement during normal flight whereby they may respond to difierential pressures above and below the wing on either side there- 0 of, yielding to superior pressures on either wing \from above, and 'maintaining the lateral stability of'the aircraft.

Other objects of the invention will appear as the following description of a preferred and practical embodiments thereof proceeds.

In the drawing which accompanies and forms a part of the following specification and throughout the several figures of which the same characters oi? reference have been designated to iden- 30 ti fy identical parts:

Figure 1 is a plan view of a portion of the Whig;

. FigureZ is a cross sectionitaken along the line 2--2 oi Figure-i;

Figure 3 is a perspective view of the underside 35 of a portion oi the wing.

The wing is constituted by a framework ii or its equivalent, provided with openings or louvres it and it, preferably setrically disposed on opposite sides of the wing and normally closed 40 by hingedpanels it and it. The panels are normally kept closed inany suitable manner as ,by the spring hinge's it. LWhen the air craft is in horizontal flight, the air pressure on the undersides oi the panels maintains them' nor- 45 mally shut, while when the aircraft is rising vertically, the pilot minimizes the resistance of the wing by opening the panels in a? positive manner, reducing ,the d portions of the wing struce ture to a mere-framework, so that as the aircraft s5 rises vertically thro theinstrumentality of the helicopter pro the displaced air may freely pass. through the opposite sides-of the swing. The means for positively opening the V panels i l and it maybe of any suitable construc- 55 u a Q Another object of the invention 'is the pro- A- practical means has-been illustrated more or less in detail in Figure 3, comprising levers l1 each including a curved arm pivotally connected to the under surfaces of the panels and a lug l8 to which an operating cable ls may be attached 5 and leading toan accessible point in the fuselage. 'Ifhe levers l'l are'connected to the panels through the intermediary of links 20 and 2|, providing lost motion so that in any operative position of the levers ll, compelled by the cables IS, the 10 panels will be capable of opening independently of said, operating means through a range limited by the throwoi the links and 2|. 1 i Independent opening movementof the panels afiords an efficient system of stabilizing control for the aircraft when in flight, under conditions frequently met with particularly in stormy weather when powerful downwardly sweeping currents strike with unequal force on the oppothe forward motion of the craft creates a pressure on the lower sides ofthe panels which holds them shut. When however a downwardly directed current of air in excess or the head resistance impinges upon the upper sides of the panels, unequally on the sides of the wing,the predominant pressure will cause the panels on one or the other side to open to a greater or has extent according to the relative value of the downward pressure. 7

This afiords a relief for the side of the wind which is overburdened permitting the aircraft to maintain its lateral equilibrium. e

- The wing is especially modified for the passage of the slip stream generated by the helicopter 40 propeller. With this end in view, the wing is provided with a circular opening it, and with suitable struts intersecting said opening and atiording support for the shaft of the helicopter propeller. 1 While I have in the above disclosure described 1 what I believe to he prantical features of the;

invention, it is-obvious that the specific details of the structure in which these features are embodied be merely by way of example and not to r beconstrued as limiting the scope of the invention as claimed.

Iclaim: v

1.'In an aeroplane provided with a helicopter propeller, a haircut and rear elongated means to urge the panels to closed position, links a mounted beneath each wing and connecting the front and rear-panel on each side, manual .con- 1 trol means to open said panels against the force link and each of said panels.

of said 'resilientmeans, and lost motion connections between the manual control means and said panels on each side whereby the panels may ,be forced downwardly by a predominance of air pressure on the upper side independently of said manual control means.

2. A wing as set forth-in claim 1 in which there is a lost motion connection between the A. SANTARSIERO. 

